Abstract: The pioneering demonstrator UAV for high-subsonic laminar flow verification adopts a special aerodynamic layout combining the inner straight section and the outer swept wing. The aerodynamic design starts with the coordination of the overall flight performance between the basic wing and the test section as well as the coordination of the high-low speed performance of the basic wing itself. According to the requirements of flight tests for high-speed flight efficiency and low-speed stall performance of the basic wing, the main control factors and design principles of high-low speed performance are analyzed, and the integrated aerodynamic design of the performance of shock waves and circulation at the cruise point as well as the separation pattern at a low-speed are conducted based on the velocity potential method with boundary-layer correction for design and numerical simulation for verification. A practical aerodynamic design of the basic wing is then created. The results of numerical simulation and the experiment prove the robustness of the design of shock-free pressure distribution under the influence of large scale nacelles. The efficient performance under the high-subsonic condition is achieved while the proper position and development order of separation as well as available lift and moment are ensured at a low speed for the basic wing at the critical angle of attack. The dual coordination of the basic wing for the demonstration requirements at the cruise point and the high-low speed performance are therefore acquired.

Key words: laminar demonstrator, unmanned aerial vehicles (UAV), trade-off design of inner and outer wings, trade-off design of high-low speed performance, cruise performance, aerodynamic stalling